WO2019093075A1 - Aube de turbine et turbine à gaz - Google Patents

Aube de turbine et turbine à gaz Download PDF

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Publication number
WO2019093075A1
WO2019093075A1 PCT/JP2018/038335 JP2018038335W WO2019093075A1 WO 2019093075 A1 WO2019093075 A1 WO 2019093075A1 JP 2018038335 W JP2018038335 W JP 2018038335W WO 2019093075 A1 WO2019093075 A1 WO 2019093075A1
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WO
WIPO (PCT)
Prior art keywords
passage
cooling
turbulator
downstream
cooling fluid
Prior art date
Application number
PCT/JP2018/038335
Other languages
English (en)
Japanese (ja)
Inventor
靖夫 宮久
進 若園
羽田　哲
Original Assignee
三菱日立パワーシステムズ株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 三菱日立パワーシステムズ株式会社 filed Critical 三菱日立パワーシステムズ株式会社
Priority to KR1020207007194A priority Critical patent/KR102350151B1/ko
Priority to DE112018004279.0T priority patent/DE112018004279B4/de
Priority to US16/651,559 priority patent/US11643935B2/en
Priority to CN201880060063.2A priority patent/CN111094701B/zh
Publication of WO2019093075A1 publication Critical patent/WO2019093075A1/fr

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer

Definitions

  • the present disclosure relates to turbine blades and gas turbines.
  • Patent Documents 1 to 3 disclose a turbine blade provided with a serpentine flow passage (serpentine flow passage) formed by a plurality of cooling passages extending along the blade height direction. . Rib-shaped turbulators are provided on the inner wall surfaces of the cooling passages of these turbine blades. The turbulator is provided for the purpose of promoting the disturbance of the flow of the cooling fluid in the cooling passage to improve the heat transfer coefficient between the cooling fluid and the turbine blade. Further, Patent Document 3 describes that a turbulator is provided so that the inclination angle formed between the turbulator (rib) and the direction of the cooling flow in each cooling passage is substantially constant. .
  • At least one embodiment of the present invention aims to provide a turbine blade and a gas turbine capable of efficiently cooling a turbine by selecting a proper turbulator.
  • a turbine blade With wings And a plurality of cooling passages respectively extending along a blade height direction inside the wing body and in communication with each other to form a serpentine flow path
  • the cooling passage is A first turbulator provided on an inner wall surface of an upstream passage of the plurality of cooling passages; A second turbulator provided on an inner wall surface of a downstream side passage disposed downstream of the upstream side passage among the plurality of cooling passages; The second angle formed by the second turbulator with respect to the flow direction of the cooling fluid in the downstream side passage than the first angle formed by the first turbulator with the flow direction of the cooling fluid in the upstream side passage Is small.
  • a turbine blade may be With wings A plurality of cooling passages extending respectively along the wing height direction inside the wing body and in communication with each other to form a serpentine flow path; A rib-shaped first turbulator provided on an inner wall surface of an upstream passage of the plurality of cooling passages; A rib-shaped second turbulator provided on an inner wall surface of a downstream passage located downstream of the upstream passage in the meandering passage among the plurality of cooling passages; The second angle formed by the second turbulator with respect to the flow direction of the cooling fluid in the downstream side passage than the first angle formed by the first turbulator with the flow direction of the cooling fluid in the upstream side passage Is small.
  • the inclination angle (second angle) of the second turbulator in the downstream passage as compared to the inclination angle (first angle) of the first turbulator in the upstream passage of the serpentine flow path Is smaller.
  • the above-mentioned heat transfer coefficient becomes relatively small in the upstream passage, and cooling of the turbine blade is suppressed, so that the temperature of the cooling fluid from the upstream passage to the downstream passage can be maintained relatively low.
  • the cooling of the turbine blade can be strengthened in the downstream region of the meandering channel because the heat transfer coefficient described above is relatively increased in the downstream side passage and the cooling of the turbine blade is promoted. As a result, the amount of the cooling fluid supplied to the serpentine flow path for cooling the turbine blades can be reduced, so that the thermal efficiency of the turbine including the gas turbine and the like can be improved.
  • the first shape factor defined by the height and the pitch of the first turbulator with respect to the flow direction of the cooling fluid in the upstream passage is smaller than the flow direction of the cooling fluid in the downstream passage.
  • a turbine blade includes: a blade body; and a plurality of blade bodies extending along the blade height direction inside the blade body and in communication with each other to form a serpentine flow path A cooling passage, the cooling passage communicating with a first turbulator provided on an inner wall surface of the upstream passage among the plurality of cooling passages, and the upstream passage among the plurality of cooling passages, And a second turbulator provided on the inner wall surface of the downstream passage located downstream of the upstream passage, and defined by the height and pitch of the first turbulator with respect to the flow direction of the cooling fluid in the upstream passage.
  • the second shape factor defined by the height and the pitch of the second turbulator with respect to the flow direction of the cooling fluid in the downstream passage is smaller than the first shape factor to be determined And features.
  • the first shape factor in the upstream passage is smaller than the second shape factor in the downstream passage. Therefore, the above-mentioned heat transfer coefficient becomes relatively small in the upstream passage, and cooling of the turbine blade is suppressed, so that the temperature of the cooling fluid from the upstream passage to the downstream passage can be maintained relatively low. Since the above-mentioned heat transfer coefficient becomes relatively large in the downstream side passage and the cooling of the turbine blade is promoted, the cooling of the turbine blade can be strengthened in the downstream side region of the turnaround flow passage. As a result, the amount of cooling fluid supplied to the return flow path for cooling the turbine blade can be reduced, so that the thermal efficiency of the turbine including the gas turbine and the like can be improved.
  • the cooling in the downstream passage is more than a first angle formed by the first turbulator with respect to the flow direction of the cooling fluid in the upstream passage.
  • the second angle formed by the second turbulator with respect to the fluid flow direction is smaller.
  • the above-mentioned heat transfer coefficient becomes relatively small in the upstream passage, and cooling of the turbine blade is suppressed, so that the temperature of the cooling fluid from the upstream passage to the downstream passage can be maintained relatively low. Since the above-mentioned heat transfer coefficient becomes relatively large in the downstream side passage and the cooling of the turbine blade is promoted, the cooling of the turbine blade can be strengthened in the downstream side region of the turnaround flow passage. As a result, the amount of cooling fluid supplied to the return flow path for cooling the turbine blade can be further reduced, so that the thermal efficiency of the turbine including the gas turbine and the like can be further improved.
  • the upstream side passage is provided with a plurality of the first turbulators arranged along the wing height direction
  • the downstream side passage is provided with a plurality of second turbulators arranged along the wing height direction
  • the average of the second angles of the plurality of second turbulators is smaller than the average of the first angles of the plurality of first turbulators.
  • the inclination angles of the plurality of second turbulators in the downstream passage are compared with the average of the inclination angles (first angles) of the plurality of first turbulators in the upstream passage of the meandering channel
  • the average of 2 angles is smaller. Therefore, as described in (1) above, the temperature of the cooling fluid from the upstream passage to the downstream passage can be maintained relatively low, and the cooling of the turbine blade in the downstream region of the serpentine flow path is strengthened can do. As a result, the amount of the cooling fluid supplied to the serpentine flow path for cooling the turbine blades can be reduced, so that the thermal efficiency of the turbine including the gas turbine and the like can be improved.
  • the upstream side passage is provided with a plurality of the first turbulators arranged along the wing height direction
  • the downstream side passage is provided with a plurality of the first turbulators arranged along the wing height direction
  • the second turbulator is provided, and an average of the second shape factors of the plurality of second turbulators is smaller than an average of the first shape factors of the plurality of first turbulators.
  • the first shape factor of some of the first turbulators is smaller than the average of the first shape factors of the other first turbulators in the same passage.
  • the first shape factor of the first turbulator at the corresponding location is smaller than the first shape factor of the other first turbulators In addition, local cooling can be enhanced.
  • the turbine blade is The first turbulator is provided in the upstream passage, and the first angle is 90 degrees.
  • the inclination angle of the turbulator in the cooling passage is in the range near 90 degrees
  • the smaller the inclination angle the larger the heat transfer coefficient between the cooling fluid and the turbine blade tends to be.
  • the inclination angle (first angle) of the first turbulator in the upstream passage is 90 degrees
  • the inclination angle (second angle) of the second turbulator in the downstream passage Is less than 90 degrees, so that the temperature of the cooling fluid from the upstream passage to the downstream passage can be kept relatively low, and the cooling of the turbine blade can be enhanced in the downstream region of the serpentine flow path .
  • the amount of the cooling fluid supplied to the serpentine flow path for cooling the turbine blades can be reduced, so that the thermal efficiency of the turbine including the gas turbine and the like can be improved.
  • the first shape factor is a pitch P1 of a pair of adjacent first turbulators among the plurality of first turbulators, and a height e1 of the pair of first turbulators based on the inner wall surface of the upstream side passage Expressed by the ratio P1 / e1 of
  • the second shape factor is a pitch P2 of a pair of adjacent second turbulators among the plurality of second turbulators, and a height e2 of the pair of second turbulators relative to the inner wall surface of the downstream side passage Is expressed by the ratio P2 / e2.
  • the ratio P / e between the pitch P of a pair of adjacent turbulators among a plurality of turbulators provided in the cooling passage and the average height e of these turbulators with reference to the inner wall surface of the cooling passage is taken as the shape factor
  • the shape factor P / e is smaller, the heat transfer coefficient between the cooling fluid and the turbine blade tends to be larger.
  • the first shape factor P1 / e1 in the upstream passage is smaller than the second shape factor P2 / e2 in the downstream passage.
  • the above-mentioned heat transfer coefficient becomes relatively small in the upstream passage, and cooling of the turbine blade is suppressed, so that the temperature of the cooling fluid from the upstream passage to the downstream passage can be maintained relatively low.
  • the cooling of the turbine blade can be strengthened in the downstream region of the meandering channel because the heat transfer coefficient described above is relatively increased in the downstream side passage and the cooling of the turbine blade is promoted.
  • the amount of cooling fluid supplied to the serpentine flow path for cooling the turbine blade can be further reduced, so that the thermal efficiency of the turbine including the gas turbine and the like can be further improved.
  • the downstream passage includes a most downstream passage located on the most downstream side in the flow direction of the cooling fluid among the plurality of cooling passages,
  • the upstream passage includes the cooling passage disposed adjacent to the most downstream passage.
  • the temperature of the cooling fluid flowing through the plurality of cooling passages forming the serpentine flow path increases toward the downstream due to heat exchange with the turbine blade to be cooled, and the most downstream side of the flow of the cooling fluid The temperature is highest in the passage.
  • the inclination angle of the turbulator is smaller than that of the upstream side passage arranged adjacent to the most downstream passage. Therefore, since the above-mentioned heat transfer coefficient becomes relatively small in the upstream side passage and cooling of the turbine blade is suppressed, it is possible to relatively maintain the temperature of the cooling fluid from the upstream side passage toward the most downstream passage.
  • the heat transfer coefficient described above is relatively increased in the most downstream passage, and the cooling of the turbine blade is promoted, the cooling of the turbine blade can be strengthened in the most downstream passage. As a result, the amount of the cooling fluid supplied to the return flow path for cooling the turbine blade can be effectively reduced, and the thermal efficiency of the turbine including the gas turbine and the like can be improved.
  • the plurality of cooling passages are serpentine flow paths including three or more of the cooling passages.
  • the plurality of cooling passages include an uppermost flow passage located on the most upstream side in the flow direction of the cooling fluid among the plurality of cooling passages,
  • the inner wall surface of the most upstream passage is formed by a smooth surface not provided with a turbulator.
  • the heat transfer coefficient between the cooling fluid and the turbine blade is smaller than when the turbulator is provided on the inner wall surface of the cooling passage.
  • the inner wall surface of the uppermost flow passage located on the most upstream side among the plurality of cooling passages is formed by the smooth surface where the turbulator is not provided.
  • the above-described heat transfer coefficient in the flow passage is smaller than the above-described heat transfer coefficient in the upstream passage. That is, the above-described heat transfer coefficient in the most upstream passage, the upstream passage, and the downstream passage that form the serpentine passage increases in this order. Therefore, the heat transfer coefficient can be easily changed stepwise in the serpentine flow path, and the cooling performance in each cooling passage can be easily adjusted.
  • the downstream passage includes a most downstream passage located on the most downstream side of the flow of the cooling fluid among the plurality of cooling passages, The most downstream passage is formed such that the flow passage area becomes smaller toward the downstream side of the flow of the cooling fluid.
  • the most downstream passage is formed such that the flow passage area becomes smaller toward the downstream side of the flow of the cooling fluid. Accordingly, the flow rate of the cooling fluid is increased. This can improve the cooling efficiency in the most downstream passage where the cooling fluid is at a relatively high temperature.
  • the downstream passage includes a most downstream passage located on the most downstream side of the flow of the cooling fluid among the plurality of cooling passages,
  • the turbine blade is
  • the system further includes a cooling fluid supply passage provided to be in communication with the upstream portion of the most downstream passage, and configured to supply cooling fluid from the outside to the most downstream passage without passing through the upstream passage.
  • the cooling fluid from the outside is separately supplied to the most downstream passage via the cooling fluid supply passage. Supplied.
  • the cooling in the most downstream passage where the cooling fluid from the upstream passage is at a relatively high temperature can be further strengthened.
  • the turbine blade is a moving blade of a gas turbine.
  • the moving blade of the gas turbine as the turbine blade has any one of the above configurations (1) to (14), the blade is supplied to the serpentine flow path for cooling the moving blade. Since the amount of cooling fluid can be reduced, the thermal efficiency of the gas turbine can be improved.
  • the turbine blade is a stationary blade of a gas turbine.
  • the stator blade of the gas turbine as the turbine blade has the configuration of any of the above (1) to (14), the gas is supplied to the serpentine flow path for cooling the stator blade. Since the amount of cooling fluid can be reduced, the thermal efficiency of the gas turbine can be improved.
  • a gas turbine according to at least one embodiment of the present invention, The turbine blade according to any one of the above (1) to (16); And a combustor for generating a combustion gas flowing in a combustion gas flow path provided with the turbine blade.
  • the turbine blade since the turbine blade has any one of the configurations (1) to (16), the amount of cooling fluid supplied to the serpentine flow path for cooling the turbine blade can be reduced. Therefore, the thermal efficiency of the gas turbine can be improved.
  • a turbine blade and a gas turbine capable of efficient cooling of a turbine are provided.
  • FIG. 2 is a partial cross-sectional view along a blade height direction of a moving blade (turbine blade) according to an embodiment. It is a figure which shows the IIB-IIB cross section of FIG. 2A.
  • FIG. 2 is a partial cross-sectional view along a blade height direction of a moving blade (turbine blade) according to an embodiment. It is a figure which shows the IIIB-IIIB cross section of FIG. 3A.
  • 1 is a schematic cross-sectional view of a moving blade (turbine blade) according to an embodiment.
  • 1 is a schematic cross-sectional view of a moving blade (turbine blade) according to an embodiment.
  • 1 is a schematic cross-sectional view of a moving blade (turbine blade) according to an embodiment.
  • 1 is a schematic cross-sectional view of a moving blade (turbine blade) according to an embodiment.
  • 1 is a schematic cross-sectional view of a moving blade (turbine blade) according to an embodiment. It is a typical sectional view of a stator blade (turbine blade) concerning one embodiment.
  • 1 is a schematic cross-sectional view of a moving blade (turbine blade) according to an embodiment.
  • a typical turbine blade is disposed in a high temperature combustion gas atmosphere, the inside of the blade is cooled with a cooling fluid to prevent thermal damage from the combustion gas of the blade.
  • the wing body is cooled by flowing a cooling fluid into a serpentine flow path (serpentine flow path) formed in the wing body.
  • a turbulence promoting member (turbulator) is disposed on the inner wall of the passage through which the cooling fluid flows. That is, the optimum turbulator is selected, and the heat transfer coefficient between the cooling fluid and the inner wall of the blade is maximized to realize the optimum cooling structure of the blade.
  • a cooling structure that reduces the passage cross-sectional area and applies a turbulator with the highest heat transfer coefficient may not be a suitable cooling structure for that blade, and a cooling structure that matches the blade shape and operating conditions of that blade. Need to be selected. For example, a blade having a blade shape having a relatively high blade height (span direction) with respect to the blade length (cord direction length), or a flow rate of the cooling fluid relatively
  • the cooling fluid is heated (heated up) in the process of flowing through the serpentine channel, and the final channel (the most downstream channel)
  • the metal temperature of may exceed the operating temperature limit.
  • the turbulator in the upstream passage upstream of the final passage selects a turbulator with low heat transfer coefficient between the flow of the cooling fluid and the wing surface, and the final passage has the highest heat transfer coefficient. It is desirable to select a turbulator. This selection suppresses heat-up of the cooling fluid flowing through the upstream passage, and in the process of flowing the cooling fluid whose heat-up is suppressed through the final passage, the application of the turbulator having a large heat transfer coefficient cools the blade by cooling fluid. Performance is improved. As a result, the metal temperature of the final passage can be suppressed to the use limit temperature or less. Further, as described above, suppressing the heat transfer coefficient is effective in reducing the pressure loss of the cooling fluid. Therefore, the combined effect of the heat-up suppressing effect of the cooling fluid and the pressure-loss reducing effect maximizes the cooling performance in the final passage.
  • the turbulator is formed by a projecting rib provided on the inner wall of the wing that forms the cooling channel.
  • the ribs are arranged at predetermined intervals in the flow direction of the cooling fluid. As the cooling fluid passes over the ribs, a vortex is generated downstream in the flow direction to promote heat transfer between the inner wall of the wing and the flow of the cooling fluid. Accordingly, there is a large difference in heat transfer coefficient between the rib inner wall with a smooth surface without ribs and the wing inner wall with ribs.
  • the factors that determine the performance and specifications of the turbulator are the tilbator inclination angle and the shape factor.
  • FIG. 13 shows the relationship between the heat transfer coefficient between the cooling fluid and the inner wall of the blade and the inclination angle of the turbulator
  • FIG. 14 shows the heat transfer coefficient between the cooling fluid and the inner wall of the wing and the turbulator Shows the relationship of the shape factor of. If the inclination angle is the optimum angle (optimum value) and the shape factor is also the optimum coefficient (optimum value) turbulator, the heat transfer coefficient is the highest and the cooling performance is the best. As a result, cooling of the inner wall surface of the wing is promoted, and the metal temperature of the cooling channel can be reduced.
  • cooling performance is suppressed in the upstream passage and cooling performance is maximized in the final passage rather than selecting a turbulator with the highest heat transfer coefficient and good cooling performance.
  • a specific wing configuration in line with this concept will be described with reference to the wing configurations of the respective embodiments described later.
  • the turbulator specifications of the upstream passage differ depending on each embodiment, but the inclination angle and the shape factor of the final passage turbulator are both selected to be optimum values. This is a configuration common to each embodiment in terms of
  • the inclination angle of the turbulator is selected to be the optimum value for all the passages.
  • the final passage selects an optimum value
  • the upstream passage upstream of the final passage selects an intermediate value.
  • the embodiment shown in FIG. 7 is an example in which the cooling performance of the upstream passage is further suppressed with respect to the cooling structure of FIG. That is, as compared with the cooling structure of FIG. 6, this embodiment is an example in which an intermediate angle (intermediate value) having a larger inclination angle than the optimal angle (optimum value) is selected as the inclination angle of the turbulator in the upstream passage. Even if the heat transfer coefficient of the upstream passage is further suppressed according to the cooling structure of FIG. 6, if the metal temperature of the upstream passage does not exceed the operating limit temperature, the cooling capacity of the final passage is increased. In the aspect of the cooling capacity of the above, the cooling structure of FIG. That is, in the cooling structure shown in FIG.
  • an intermediate value is selected in which the inclination angles of the turbulators of all the upstream passages on the upstream side of the final passage are larger than the inclination angles (optimum values) of the turbulators of the final passage.
  • different intermediate values are selected for the inclination angles of the respective passages.
  • the inclination angle of the turbulators of the most upstream passage in the upstream passages is smaller than 90 degrees, and is selected so that the inclination angles of the turbulators of each upstream passage gradually decrease as the final passage is approached.
  • the shape factor of the turbulator the same intermediate value is selected in the upstream passage as the same configuration as the cooling structure of FIG. 6 and the optimum value is selected in the final passage.
  • the embodiment shown in FIG. 8 is an example in which the cooling performance of the upstream passage is further suppressed with respect to the cooling structure of FIG. 7. That is, even in the case of the cooling structure shown in FIG. 8, if the metal temperature of the upstream passage does not exceed the use limit temperature, the cooling capability of the final passage is further increased. That is, in the cooling structure shown in FIG. 8, the inclination angle of the turbulators in the upstream passage is made uniform at 90 degrees, and only the inclination angle of the turbulators in the final passage is the optimum value. Further, as the shape factor of the turbulator, as the same configuration as the cooling structure of FIG. 6, an intermediate value is selected in the upstream passage, and an optimum value is selected in the final passage.
  • the embodiment shown in FIG. 9 is an embodiment in which the cooling performance of the upstream passage is further suppressed with respect to the cooling structure of FIG. That is, in the wing configuration shown in the present embodiment, no turbulator is disposed in the most upstream side passage of the upstream side passage, and the inner wall of the passage is formed as a smooth surface. Even if the metal temperature of the most upstream passage is a smooth surface without a turbulator, if the metal temperature is lower than the operating limit temperature, the heat-up of the cooling fluid is further suppressed, and the cooling capacity of the final passage is further increased. Is born. That is, in the structure shown in FIG.
  • the most upstream side passage is a smooth surface
  • the inclination angles of the turbulators of the other upstream side passages excluding the most upstream side passage are selected as intermediate values
  • the shape factor of the turbulator is as shown in FIG.
  • An intermediate value with the same configuration is selected.
  • the inclination angle and the shape factor of the final passage turbulator are the same as in the configuration of FIG.
  • the embodiment shown in FIG. 10 is an embodiment in which the cooling performance of the upstream passage is further suppressed with respect to the cooling structure of FIG. It is common to the embodiment of FIG. 9 in that the most upstream side passage is formed by a smooth surface and is not provided with a turbulator. However, it differs from the cooling structure shown in FIG. 9 in that the inclination angles of the turbulators of the two other upstream passages adjacent to the most upstream passage are 90 degrees. The inclination angle of the turbulators of the upstream side passage adjacent to the final passage is the same as the structure shown in FIG. Further, the inclination angle and the shape factor of the final passage turbulator are the same as the configuration shown in FIG.
  • FIG. 11 is an example in which the basic concept of the present invention is applied to a vane.
  • the inlet of the cooling fluid supplied to the serpentine flow path is radially outward of the blade, and the radial flow direction of the cooling fluid flowing through the final passage is the reverse direction to the moving blade.
  • the inclination angle and the shape factor of the turbulator are the same as in FIG.
  • FIG. 1 is a schematic configuration diagram of a gas turbine to which a turbine blade according to an embodiment is applied.
  • the gas turbine 1 is rotationally driven by the compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and the combustion gas.
  • a turbine 6 configured as described above.
  • a generator (not shown) is connected to the turbine 6.
  • the compressor 2 includes a plurality of stationary blades 16 fixed to the compressor casing 10 and a plurality of moving blades 18 implanted in the rotor 8 so as to be alternately arranged with respect to the stationary blades 16. .
  • the air taken in from the air intake 12 is sent to the compressor 2, and this air is compressed by passing through the plurality of stationary blades 16 and the plurality of moving blades 18. Become compressed air.
  • the fuel and the compressed air generated by the compressor 2 are supplied to the combustor 4, and the fuel and the compressed air are mixed and burned in the combustor 4, and the working fluid of the turbine 6 is supplied. A combustion gas is generated.
  • a plurality of combustors 4 may be disposed in the casing 20 along the circumferential direction centering on the rotor.
  • the turbine 6 has a combustion gas flow passage 28 formed in the turbine casing 22, and includes a plurality of stationary blades 24 and moving blades 26 provided in the combustion gas flow passage 28.
  • the stator vanes 24 are fixed to the turbine casing 22 side, and a plurality of stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row.
  • the moving blades 26 are implanted in the rotor 8, and a plurality of moving blades 26 arranged along the circumferential direction of the rotor 8 constitute a moving blade row.
  • the stationary blade row and the moving blade row are alternately arranged in the axial direction of the rotor 8.
  • the combustion gas from the combustor 4 that has flowed into the combustion gas flow path 28 passes through the plurality of stationary blades 24 and the plurality of moving blades 26 to rotationally drive the rotor 8, thereby connecting to the rotor 8.
  • the generated generator is driven to generate electric power.
  • the combustion gas after driving the turbine 6 is exhausted to the outside through the exhaust chamber 30.
  • At least one of the blades 26 or the vanes 24 of the turbine 6 is a turbine blade 40 described below.
  • the following description will be mainly made with reference to the drawing of the moving blade 26 as the turbine blade 40, but basically the same description can be applied to the stationary blade 24 as the turbine blade 40.
  • FIGS. 2A and 3A are partial cross-sectional views along the blade height direction of the moving blade 26 (the turbine blade 40) according to an embodiment
  • FIGS. 2B and 3B are respectively a view taken along line IIIA- of FIG. It is a figure which shows an IIIA cross section and a IIIB-IIIB cross section. The arrows in the figure indicate the flow direction of the cooling fluid.
  • the moving blade 26, which is the turbine blade 40 according to one embodiment, includes a blade body 42, a platform 80, and a blade root portion 82.
  • the blade root 82 is embedded in the rotor 8 (see FIG. 1), and the moving blades 26 rotate with the rotor 8.
  • the platform 80 is integrally configured with the wing root 82.
  • the wing body 42 is provided to extend along the radial direction (hereinafter, sometimes simply referred to as “radial direction” or “span direction”) of the rotor 8 and is a proximal end fixed to the platform 80 A tip comprising a top plate 49 positioned on the opposite side (radial direction outer side) from the base end 50 in the blade height direction (radial direction of the rotor 8) and the top end 49 of the wing body 42 And 48 (end 2).
  • the blade body 42 of the moving blade 26 has a leading edge 44 and a trailing edge 46 from the base end 50 to the tip end 48, and the wing surface of the blade body 42 has a blade height between the base end 50 and the tip end 48 It includes a pressure surface (abdominal surface) 56 and a suction surface (back surface) 58 extending along the longitudinal direction.
  • a cooling flow passage for flowing a cooling fluid (for example, air) for cooling the turbine blade 40 is provided inside the wing body 42.
  • the wing body 42 includes a meandering channel 61 and a leading edge side channel 36 located closer to the leading edge 44 than the meandering channel 61 as a cooling channel. Is formed. Cooling fluid from the outside is supplied to the return flow passage 61 and the front edge side flow passage 36 via the inner flow passages 84 and 35, respectively.
  • the cooling flow channels such as the meandering flow channel 61 and the front edge side flow channel 36, a blade provided in the combustion gas flow channel 28 of the turbine 6 and exposed to high temperature combustion gas It is designed to cool 42.
  • meandering channel 61 includes a plurality of cooling passages 60a, 60b, 60c... (Hereinafter collectively referred to as "cooling passage 60") extending along the blade height direction.
  • a plurality of ribs 32 are provided in the blade body 42 of the turbine blade 40 along the blade height direction, and adjacent cooling passages 60 are partitioned by the ribs 32.
  • the meandering channel 61 includes three cooling passages 60a to 60c, and the cooling passages 60a to 60c extend from the front edge 44 side to the rear edge 46 side. It is arranged in order.
  • the folded flow passage 61 includes five cooling passages 60a to 60e, and the cooling passages 60a to 60e extend from the front edge 44 side to the rear edge 46 side. They are arranged in this order.
  • the cooling passages (for example, the cooling passage 60a and the cooling passage 60b) adjacent to each other among the plurality of cooling passages 60 forming the serpentine flow passage 61 are connected to each other at the distal end 48 side or the proximal end 50 side.
  • a return flow path is formed in which the flow direction of the fluid is reversed in the wing height direction, and the entire serpentine flow path 61 has a shape that meanders in the radial direction. That is, the plurality of cooling passages 60 communicate with each other to form a serpentine passage (serpentine passage) 61.
  • the plurality of cooling passages 60 forming the serpentine flow passage 61 includes the most upstream passage located on the most upstream side of the plurality of cooling passages 60 and the most downstream passage located on the most downstream side.
  • the cooling passage 60a located on the most front edge 44 side among the plurality of cooling passages 60 is the most upstream passage 65, and the cooling passage located on the most trailing edge 46 side.
  • 60c (FIGS. 2A to 2B) or the cooling passage 60e (FIGS. 3A to 3B) is the most downstream passage 66.
  • the cooling fluid is, for example, an internal flow channel 84 formed inside the blade root 82 and an inlet opening 62 provided on the base end 50 side of the blade 42 (FIG. 2A).
  • FIG. 3A is introduced into the most upstream passage 65 of the serpentine flow passage 61, and sequentially flows downstream through the plurality of cooling passages 60.
  • the cooling fluid flowing through the most downstream passage 66 most downstream in the flow direction of the cooling fluid among the plurality of cooling passages 60 passes through the outlet opening 64 provided on the tip 48 side of the blade body 42 and the cooling fluid of the turbine blade 40. It flows out to the outside combustion gas channel 28.
  • the outlet opening 64 is an opening formed in the top plate 49, and a part of the cooling fluid flowing through the most downstream passage 66 is discharged from the outlet opening 64.
  • a stagnant space of the cooling fluid is generated in the space near the top plate 49 of the most downstream passage 66, and the inner wall surface 63 of the top plate 49 can be suppressed from being overheated.
  • the shape of the return channel 61 is not limited to the shape shown in FIGS. 2A to 3B.
  • a plurality of folded flow paths may be formed inside the blade body 42 of one turbine blade 40.
  • the meandering channel 61 may be branched into a plurality of channels at a branch point on the meandering channel 61.
  • the trailing edge 47 (portion including the trailing edge 46) of the wing body 42 has a plurality of coolings arranged along the wing height direction.
  • a hole 70 is formed.
  • the plurality of cooling holes 70 communicate with the cooling flow passage (the most downstream passage 66 of the meandering flow passage 61 in the illustrated example) formed inside the wing 42 and the surface at the rear edge 47 of the wing 42 It is open to
  • a portion of the cooling fluid flowing through the cooling flow passage (the most downstream passage 66 of the serpentine flow passage 61 in the illustrated example) passes through the cooling holes 70 to open the turbine blade 40 from the opening of the trailing edge 47 of the blade 42. Flow out to the combustion gas flow path 28 outside the Thus, the trailing edge portion 47 of the wing body 42 is convectively cooled by the passage of the cooling fluid through the cooling holes 70.
  • Rib-shaped turbulators 34 are provided on at least some of the inner wall surfaces 63 of the plurality of cooling passages 60. In the exemplary embodiment shown in FIGS. 2A-3B, a plurality of turbulators 34 are provided on the inner wall surface 63 of each of the plurality of cooling passages 60.
  • FIGS. 4 and 5 are each a schematic view for explaining the configuration of the turbulator 34 according to one embodiment, and FIG. 4 is a blade height direction of the turbine blade 40 shown in FIGS. 2A to 3B.
  • FIG. 4 is a schematic view of a partial cross section along a plane including the blade thickness direction (the circumferential direction of the rotor 8), and FIG. 4 is a blade height direction and a blade width of the turbine blade 40 shown in FIGS.
  • FIG. 7 is a schematic view of a partial cross section along a plane including a direction (axial direction of the rotor 8).
  • each turbulator 34 is provided on the inner wall surface 63 of the cooling passage 60, and the height of the turbulator 34 based on the inner wall surface 63 is e. Further, as shown in FIGS. 4 and 5, in the cooling passage 60, the plurality of turbulators 34 are provided at intervals of the pitch P. Further, as shown in FIG. 5, an angle (hereinafter also referred to as “inclination angle”) forming an acute angle between each of the turbulators 34 and the flow direction of the cooling fluid in the cooling passage 60 (arrow LF in FIG. 5). , The inclination angle ⁇ .
  • the turbulence of the flow such as the generation of a vortex is promoted in the vicinity of the turbulator 34. That is, the cooling fluid having passed over the turbulator 34 forms a vortex between the adjacent turbulators 34 disposed downstream. Thereby, the vortex flow of the cooling fluid adheres to the inner wall surface 63 of the cooling passage 60 near the intermediate position between the turbulators 34 adjacent to each other in the flow direction of the cooling fluid, and the heat transfer coefficient between the cooling fluid and the wing body 42 Of the turbine blade 40 can be effectively cooled.
  • the generation state of the swirling flow of the cooling fluid changes, which affects the heat transfer coefficient with the inner wall of the wing.
  • the vortex may not adhere to the inner wall surface 63. Therefore, an appropriate range exists between the heat transfer coefficient and the inclination angle of the turbulator and the ratio between the heat transfer coefficient and the pitch and the height as described later.
  • the height of the turbulator is too high, it causes an increase in pressure loss of the cooling fluid.
  • FIGS. 6 to 10 and 12 are schematic cross-sectional views of the moving blade 26 (turbine blade 40) according to one embodiment.
  • FIG. 11 is a schematic cross-sectional view of the stationary blade 24 (turbine blade 40) according to an embodiment.
  • the arrows in the figure indicate the flow direction of the cooling fluid.
  • the moving blade 26 shown in FIGS. 6 to 10 and 12 has the same configuration as the moving blade 26 described above.
  • meandering flow paths 61 formed in the turbine blade 40 shown in FIGS. 6 to 12 are each formed by five cooling passages 60a to 60e, and among these, the cooling located closest to the front edge 44 side
  • the passage 60 a is the most upstream passage 65
  • the cooling passage 60 e located closest to the trailing edge 46 is the most downstream passage 66.
  • the stator blade 24 (turbine blade 40) according to an embodiment includes a blade body 42, an inner shroud 86 positioned radially inward with respect to the blade body 42, and the blade body 42. And an outer shroud 88 located radially outward.
  • the outer shroud 88 is supported by the turbine casing 22 (see FIG. 1), and the vanes 24 are supported by the turbine casing 22 via the outer shroud 88.
  • the wing body 42 has an outer end 52 located on the outer shroud 88 side (i.e., radially outer side) and an inner end 54 located on the inner shroud 86 side (i.e., radially inner side).
  • the wing body 42 of the vane 24 has a leading edge 44 and a trailing edge 46 from the outer end 52 to the inner end 54, and the wing surface of the wing body 42 has a wing height between the outer end 52 and the inner end 54. It includes a pressure surface (abdominal surface) 56 and a suction surface (back surface) 58 extending along the longitudinal direction.
  • a meandering channel 61 formed of a plurality of cooling passages 60 is formed inside the wing body 42 of the stationary blade 24, and the meandering channel 61 has the same configuration as the meandering channel 61 in the moving blade 26 described above.
  • a serpentine flow passage 61 is formed by five cooling passages 60a to 60e.
  • the cooling fluid is provided by an internal flow passage (not shown) formed inside the outer shroud 88 and an inlet opening 62 provided on the outer end 52 side of the blade 42.
  • the cooling fluid flowing through the most downstream passage 66 most downstream in the flow direction of the cooling fluid among the plurality of cooling passages 60 is an outlet opening provided on the inner end 54 side (inner shroud 86 side) of the wing body 42.
  • the gas flows out to the combustion gas flow path 28 outside the stationary blade 24 (the turbine blade 40) via the nozzle 64, or is discharged into the combustion gas from the cooling holes 70 of the trailing edge 47 described later.
  • the turbulator 34 described above is provided on the inner wall surface of at least some of the plurality of cooling passages 60.
  • a plurality of turbulators 34 are provided on the inner wall surface of each of the plurality of cooling passages 60.
  • a plurality of cooling holes 70 may be formed at the rear edge 47 of the wing body 42 so as to be arranged along the wing height direction.
  • the inclination angles of the turbulator 34 in each of the cooling passages 60a to 60e are ⁇ a, ⁇ b, ⁇ c, ⁇ d, and ⁇ e, respectively, and each of the cooling passages 60a to 60e
  • Pa, Pb, Pc, Pd, Pe be the pitches of the adjacent turbulators 34 in the above, respectively, and the height (or average height) of the adjacent turbulators 34 in each passage be each of ea, eb, ec, ed, It is ee.
  • the pitch of the turbulators 34 in the cooling passages 60a to 60e of the moving blade 26 shown in FIG. 12 will be described later.
  • the turbulator 34 is not provided in the cooling passage 60a of the moving blade 26 shown in FIGS. 9 to 10, and the inner wall surface of the cooling passage 60a is formed by a smooth surface.
  • the rib-like first turbulator (turbulator 34) provided on the inner wall surface of the upstream passage among the plurality of cooling passages 60 and the upstream side of the meandering channel 61 among the plurality of cooling passages 60
  • a rib-like second turbulator (turbulator 34) provided on the inner wall surface of the downstream side passage located downstream of the passage. Then, a second angle formed by the second turbulator with respect to the flow direction of the cooling fluid in the downstream side passage than the first angle ⁇ 1 (inclination angle) formed by the first turbulator with the flow direction of the cooling fluid in the upstream side passage ⁇ 2 (inclination angle) is smaller.
  • the plurality of cooling passages 60 are an upstream side passage provided with a first turbulator having an inclination angle of a first angle ⁇ 1, and a second turbulator having an inclination angle of a second angle ⁇ 2 smaller than the first angle ⁇ 1. And a downstream passage provided.
  • the turbine blades 40 (moving blades 26 or stator blades 24) shown in FIGS. 7 to 8 and 9 to 11 are turbine blades according to the present embodiment.
  • the cooling passages 60d to 60e, which are ⁇ 2), are the above-mentioned downstream passages.
  • the cooling passage 60c is the upstream passage whose inclination angle is the first angle ⁇ 1 ( ⁇ c)
  • the cooling passages 60d to 60e are downstream passages whose inclination angle is the second angle ⁇ 2 ( ⁇ 1). is there.
  • the cooling passage 60d is the upstream passage whose inclination angle is the first angle ⁇ 1 ( ⁇ d)
  • the cooling passage 60e is a downstream passage whose inclination angle is the second angle ⁇ 2 ( ⁇ 1). is there.
  • the “upstream passage” and the “downstream passage” indicate the relative positional relationship between the two cooling passages 60 among the plurality of cooling passages 60.
  • FIG. 13 is a graph showing an example of the correlation between the heat transfer coefficient ratio ⁇ and the inclination angle ⁇ of the turbulator.
  • the heat transfer coefficient ratio ⁇ is provided with a heat transfer coefficient h between the cooling fluid in the cooling passage and the turbine blade when the turbulator is provided on the inner wall surface of the cooling passage, and a turbulator is provided in the cooling passage.
  • the ratio h / h0 of the heat transfer coefficient h0 between the cooling fluid and the turbine blade in the cooling passage when the inner wall surface of the cooling passage is formed as a smooth surface.
  • the heat transfer coefficient h between the cooling fluid and the turbine blade 40 tends to be larger as the inclination angle ⁇ is smaller.
  • the inclination angle ⁇ of the turbulator 34 increases, the pressure loss of the cooling fluid flowing through the passage decreases. Therefore, it is important to select the inclination angle ⁇ of the turbulator 34 while balancing the increase of the heat transfer coefficient and the increase of the pressure loss by decreasing the inclination angle ⁇ . Note that, as shown in FIG. 13, the inclination angle ⁇ has an optimum angle at which the heat transfer coefficient ratio ⁇ is the highest.
  • this inclination angle ⁇ is called an optimum angle (optimum value).
  • One example of the optimum angle is 60 degrees.
  • an inclination angle at which the heat transfer coefficient becomes smaller than the heat transfer coefficient ratio ⁇ at the optimum angle is called an intermediate angle (intermediate value).
  • the inclination angle (second angle ⁇ 2) of the second turbulator in the downstream passage is compared with the inclination angle (first angle ⁇ 1) of the first turbulator in the upstream passage of the serpentine flow path 61 It is smaller.
  • the optimum angle (optimum value) is selected as the inclination angle (second angle ⁇ 2) of the second turbulator
  • the middle angle (intermediate value) is selected as the inclination angle (first angle ⁇ 1) of the first turbulator.
  • the heat transfer coefficient h (or the heat transfer coefficient ratio ⁇ ) becomes relatively small in the upstream passage, and the cooling of the turbine blade 40 is suppressed, so the temperature of the cooling fluid going from the upstream passage to the downstream passage Can be kept relatively low.
  • the above-described heat transfer coefficient h (or heat transfer coefficient ratio ⁇ ) becomes relatively large in the downstream side passage, and the cooling of the turbine blade 40 is promoted. Cooling can be enhanced. As a result, the amount of the cooling fluid supplied to the meandering channel 61 for cooling the turbine blade 40 can be reduced, so the thermal efficiency of the turbine 6 can be improved.
  • the average of the second angles ⁇ 2 of the plurality of second turbulators (turbulators 34) is smaller than the average of the first angles ⁇ 1 of the plurality of first turbulators (turbulators 34).
  • the temperature of the cooling fluid from the upstream passage to the downstream passage can be maintained relatively low, and the cooling of the turbine blade 40 in the downstream region of the serpentine flow passage 61 can be performed. It can be strengthened. As a result, the amount of the cooling fluid supplied to the meandering channel 61 for cooling the turbine blade 40 can be reduced, so the thermal efficiency of the turbine 6 can be improved.
  • the turbine blade 40 is provided in the upstream passage, and a first turbulator (the first A turbulator 34) is provided. That is, any one of the cooling passage 60a in FIG. 7, the cooling passages 60a to 60d in FIG. 8, the cooling passage 60b or 60c in FIG. 10, or any of 60a to 60d in FIG. And the at least one cooling passage 60 located downstream of each of the upstream passages may be the downstream passage.
  • the inclination angle ⁇ of the turbulator 34 in the cooling passage 60 is in the range of 90 degrees or less than 90 degrees, the smaller the inclination angle ⁇ , the heat transfer coefficient h between the cooling fluid and the turbine blade 40 (or The transmission ratio ⁇ ) tends to be large.
  • the inclination angle (first angle ⁇ 1) of the first turbulator in the upstream passage is 90 degrees
  • the inclination angle (second angle ⁇ 2) of the second turbulator in the downstream passage is 90 Less than. Therefore, the temperature of the cooling fluid from the upstream passage to the downstream passage can be maintained relatively low, and the cooling of the turbine blade 40 can be strengthened in the downstream region of the serpentine flow passage 61. As a result, the amount of the cooling fluid supplied to the meandering channel 61 for cooling the turbine blade 40 can be reduced, so the thermal efficiency of the gas turbine 1 can be improved.
  • the pitch P of a pair of adjacent turbulators 34 (see FIGS. 4 and 5) and the height e (or a pair of turbulators) of the turbulators 34 with reference to the inner wall surface 63 of the cooling passage 60.
  • the ratio P / e to the average height e) of 34 is defined as the shape factor.
  • the second shape factor P2 / e2 of is smaller.
  • the first shape factor P1 / e1 is the pitch P1 of a pair of adjacent first turbulators among the plurality of first turbulators (turbulators 34) and the height e1 of the first turbulator (or the pair of first turbulators)
  • the second shape factor P2 / e2 is the pitch P2 of a pair of adjacent second turbulators among the plurality of second turbulators (turbulators 34) and the height e2 of the second turbulator (or a pair of second turbulators)
  • the turbine blades 40 (moving blades 26 or stator blades 24) shown in FIGS. 6 to 12 are turbine blades according to the present embodiment.
  • the shape factor Pe / ee of the cooling passage 60e is the shape factor of the cooling passages 60a-60d located upstream of the cooling passage 60e. It is smaller than (Pa / ea to Pd / ed).
  • the shape factor Pe / ee of the cooling passage 60e is the shape factor (Pb / eb to Pd /) of the cooling passages 60b to 60d located upstream of the cooling passage 60e. less than ed).
  • the cooling passage 60e is a downstream passage having a second shape coefficient P2 / e2 (Pe / ee) having a small shape coefficient of the turbulator 34, and is positioned upstream of the downstream passage (cooling passage 60e)
  • the cooling passage 60a having a first shape factor P1 / e1 (Pa / ea to Pd / ed or Pb / eb to Pd / ed) in which the shape factor of the turbulator 34 is larger than the second shape factor P1 / e2.
  • 60d or the cooling passages 60b to 60d are upstream passages.
  • FIG. 14 is a graph showing an example of the correlation between the heat transfer coefficient ratio ⁇ and the shape factor P / e of the turbulator.
  • the heat transfer coefficient ratio ⁇ is the ratio h / h0 of the above-described heat transfer coefficient h and heat transfer coefficient h0.
  • the smaller the shape factor P / e of the turbulator 34 in the cooling passage 60 the larger the heat transfer coefficient ratio ⁇ between the cooling fluid and the turbine blade 40, and the space between the cooling fluid and the turbine blade 40.
  • the heat transfer coefficient h tends to be large.
  • the shape factor P / e of the turbulator 34 is reduced, the pressure loss of the cooling fluid flowing through the passage tends to increase.
  • the shape factor P / e decreases but the pressure loss of the cooling fluid increases. Therefore, it is important to select the shape factor P / e of the turbulator 34 while balancing the increase in heat transfer coefficient and the increase in pressure loss by reducing the shape factor P / e.
  • the optimum shape factor that maximizes the heat transfer coefficient ratio ⁇ is referred to as the optimum coefficient (optimum value) for the sake of convenience.
  • a shape factor P / e in which the shape factor P / e is larger than the optimum coefficient and the heat transfer coefficient ratio ⁇ is smaller than the shape factor P / e of the optimum coefficient is called an intermediate coefficient (intermediate value).
  • the first shape factor P1 / e1 in the upstream passage is larger than the second shape factor P2 / e2 in the downstream passage.
  • an optimum coefficient is selected as the shape factor (second shape factor) of the second turbulator, and an intermediate coefficient is selected as the shape factor (first shape factor) of the first turbulator. Therefore, the heat transfer coefficient h (or the heat transfer coefficient ratio ⁇ ) becomes relatively small in the upstream passage, and the cooling of the turbine blade 40 is suppressed, so the temperature of the cooling fluid going from the upstream passage to the downstream passage Can be kept relatively low.
  • the above-described heat transfer coefficient h (or heat transfer coefficient ratio ⁇ ) becomes relatively large in the downstream side passage, and the cooling of the turbine blade 40 is promoted. Cooling can be enhanced. As a result, the amount of the cooling fluid supplied to the meandering channel 61 for cooling the turbine blade 40 can be reduced, so the thermal efficiency of the gas turbine 1 can be improved.
  • the shape factor P / e of the turbulator 34 is represented by the ratio P / e of the pitch P of the pair of turbulators 34 adjacent to the height e of the turbulator 34.
  • the heat transfer coefficient h heat transfer coefficient ratio ⁇
  • the shape factor P / e can be changed to select a target heat transfer coefficient h.
  • the height e of the turbulator is related not only to the shape factor P / e, but also to the width T (see FIG. 4) of the passage.
  • the pressure loss of the cooling fluid flowing in the passage is increased.
  • the downstream passage includes the most downstream passage 66 of the plurality of cooling passages 60 located on the most downstream side of the flow of the cooling fluid, and the upstream passage is adjacent to the most downstream passage 66 It includes a cooling passage 60 disposed.
  • the cooling passage 60e (the most downstream passage 66) located on the most downstream side among the plurality of cooling passages 60 is the downstream passage and the upstream passage is A cooling passage 60d is disposed adjacent to the cooling passage 60e (the most downstream passage 66).
  • the cooling fluid flowing through the plurality of cooling passages 60 forming the serpentine flow path 61 is heated up by heat exchange with the turbine blade 40 to be cooled, and the temperature rises toward the downstream, and the cooling fluid flow direction most The temperature is highest in the most downstream passage 66 located downstream.
  • the inclination angle of the turbulator 34 is smaller than that of the upstream passage, or the shape factor P / e of the turbulator 34 is smaller than that of the upstream passage. small.
  • the heat transfer coefficient h (or heat transfer coefficient ratio ⁇ ) described above becomes relatively small in the upstream passage, and the cooling of the turbine blade 40 is suppressed, so the temperature of the cooling fluid from the upstream passage to the most downstream passage Can be kept relatively low.
  • the heat transfer coefficient h (or heat transfer coefficient ratio ⁇ ) mentioned above is relatively increased in the most downstream passage and cooling of the turbine blade 40 is promoted, the cooling of the turbine blade 40 in the most downstream passage is strengthened. Can. Thereby, the amount of the cooling fluid supplied to the meandering channel 61 for cooling the turbine blade 40 can be effectively reduced, and the thermal efficiency of the gas turbine 1 can be improved.
  • the plurality of cooling passages 60 may include three or more cooling passages 60.
  • the plurality of cooling passages 60 may include five or more cooling passages 60, as shown, for example, in FIGS. 3A-3B and 6-12.
  • the inclination angle (first angle ⁇ 1) of the first turbulator in the upstream passage of the cooling passages 60 forming three or five or more passes forming the meandering passage 61 cooling by these three or five passes or more
  • the inclination angle (second angle ⁇ 2) of the second turbulator in the downstream passage of the passage 60 can be made smaller.
  • the shape coefficient P2 / e2 of the second turbulator in the downstream passage among the cooling passages 60 of these three or more than five passes is made smaller than the shape coefficient P1 / e1 of the first turbulator in the upstream passage.
  • the amount of the cooling fluid supplied to the meandering channel 61 for cooling the turbine blade 40 can be reduced, so the thermal efficiency of the gas turbine 1 can be improved.
  • the passage cross-sectional area of each cooling passage 60 is reduced, whereby the flow velocity of the cooling fluid And the cooling of the turbine blade 40 can be promoted.
  • the number of cooling passages 60 is increased by setting the number of cooling passages 60 forming the meandering passage 61 to three or more passes, the number of ribs 32 provided between the adjacent cooling passages 60 also increases. The surface area in contact with the cooling fluid out of 40 is increased.
  • the cross-sectional average temperature of the turbine blade 40 can be effectively reduced, and the margin of the cross-sectional average creep strength is increased, so the amount of cooling fluid can be reduced.
  • the inner wall surface of the most upstream passage 65 located on the most upstream side of the flow direction of the cooling fluid among the plurality of cooling passages 60 is provided with a turbulator. Not formed by the smooth surface 67.
  • the heat between the cooling fluid and the turbine blade 40 is provided as compared with the case where the turbulator is provided on the inner wall surface of the cooling passage 60.
  • the above-described heat transfer coefficient h (or heat transfer coefficient ratio ⁇ ) in the most upstream passage 65 forming the meandering flow passage 61, the upstream passage, and the downstream passage increases in this order. Therefore, the heat transfer coefficient h (or the heat transfer coefficient ratio ⁇ ) can be easily changed stepwise in the meandering channel 61, and the cooling performance in each of the cooling passages 60 can be easily adjusted.
  • the downstream passage includes the most downstream passage 66 of the plurality of cooling passages 60 located on the most downstream side in the flow direction of the cooling fluid, and the most downstream passage 66 has the flow direction of the cooling fluid
  • the channel cross-sectional area is formed to be smaller toward the downstream side of the
  • the most downstream passage 66 has an inclination angle ⁇ or a shape factor P of the turbulator 34 relative to the cooling passage 60 located upstream of the most downstream passage 66.
  • / E is a small downstream passage.
  • the most downstream passage 66 is the upstream side (the base end 50 side (end 1) of the wing body 42) in the flow direction of the cooling fluid in the most downstream passage 66 and the downstream side (end side of the wing 42 (end).
  • the channel cross-sectional area is formed to be smaller toward the part 2).
  • the cooling passage 60d adjacent to the most downstream passage 66 and in communication with the most downstream passage 66 is a cooling passage from the upstream side (the tip 48 side of the wing 42) of the flow direction of the cooling fluid
  • the flow path cross-sectional area is formed to be smaller toward the proximal end 50 side of 42).
  • the cooling fluid according to the most downstream passage 66 follows the downstream side. Flow rate is increased.
  • the cooling passage 60d is formed such that the cross-sectional area of the flow passage becomes smaller toward the downstream side in the flow direction of the cooling fluid, similarly to the most downstream passage 66, the cooling passage 60d goes downstream The flow rate of the cooling fluid is increased accordingly. Accordingly, it is possible to suppress an increase in metal temperature of the blade inner wall on the side of the base end 50 which is the downstream side of the cooling passage 66d.
  • the flow passage cross-sectional area of the most downstream passage 66 is formed to be smaller toward the tip 48 side that is the downstream side in the flow direction of the cooling fluid, the flow velocity of the cooling fluid increases and Can be cooled efficiently. As a result, the rise in metal temperature of the inner wall of the blade of the most downstream passage 66 is suppressed, and the cooling efficiency in the most downstream passage 66 where the temperature of the cooling fluid is relatively high can be improved.
  • the above description is for the wing configuration of FIG. 3A, but changes in the flow passage cross-sectional area in the most downstream passage 66 and the cooling passage 60b in the wing configuration shown in FIG. 2A can be similarly described. Further, even in the case of the stator blade 26 shown in the schematic view of FIG.
  • the downstream inner end 54 (end 2) of the cooling fluid in the flow direction from the outer end 52 (end 1) of the most downstream passage 66 may be formed to be smaller toward the end. As a result, the flow velocity of the cooling fluid is increased, and an increase in the metal temperature of the inner wall of the most downstream passage 66 can be suppressed.
  • the downstream passage includes the most downstream passage 66 of the plurality of cooling passages 60 located on the most downstream side in the flow direction of the cooling fluid, and the turbine blade 40 is upstream of the most downstream passage 66
  • a cooling fluid supply passage 92 provided to be in communication with the unit and configured to supply the cooling fluid from the outside to the most downstream passage 66 (downstream passage) without passing through the upstream passage.
  • the inside of the blade root 82 is in communication with the upstream portion (the proximal end 50 side of the blade 42) of the most downstream passage 66 which is the downstream passage.
  • a cooling fluid supply passage 92 is provided.
  • the cooling fluid from the outside does not pass through the upstream passage (at least one of the cooling passages 60a to 60d) located upstream of the most downstream passage 66, and the cooling fluid from the cooling fluid supply passage 92
  • the downstream passage 66 can be supplied.
  • the cooling fluid from the outside is separately supplied to the most downstream passage 66 via the cooling fluid supply passage 92.
  • the flow rate of the cooling fluid supplied and flowing through the most downstream passage increases. Therefore, the cooling in the most downstream passage 66 where the cooling fluid from the upstream passage of the serpentine passage 61 is relatively hot can be further strengthened.
  • the stationary blades 24 (turbine blades 40) shown in FIG. 11 have the configuration of the turbulator 34 corresponding to the moving blades 26 (turbine blades 40) shown in FIG. 8 (inclination angle ⁇ or shape factor P / e in each cooling passage 60).
  • the stator blade 24 (turbine blade 40) according to some embodiments is the moving blade 26 (turbine shown in FIG. 6, FIG. 7, FIG. 9, FIG. 10 and FIG. It may have a configuration corresponding to any of the wings 40).
  • the first passage comprising a first turbulator, wherein the first shape factor of some of the first turbulators is the first shape of the other first turbulators in the same passage Less than the average of the coefficients.
  • the first shape factor of the first turbulator provided in the most downstream cooling passage 60 d of the upstream passages is the first shape factor or a plurality of other first turbulators in the same passage.
  • a coefficient smaller than the average value of the first shape coefficients of the other first turbulators is selected. For example, a hot spot may be generated in a part of the same passage of the most downstream cooling passage 60d, and the metal temperature of the wing inner wall may be locally higher than other wing inner walls.
  • the pitch P is reduced without changing the height e of the turbulator 34a of the corresponding inner wall, and the first shape factor P / e of the turbulator 34 is reduced. That is, the first shape factor of the first turbulator on the inner wall of the passage where the hot spot is generated is made smaller than that at other places to increase the heat transfer coefficient h, and the cooling can be partially reinforced.
  • FIG. 12 shows the example of the cooling passage 66d, the invention is not limited to this embodiment, and may be applied to other upstream passages.
  • a representation representing a relative or absolute arrangement such as “in a direction”, “along a direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial”
  • a representation representing a relative or absolute arrangement such as “in a direction”, “along a direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial”
  • expressions that indicate that things such as “identical”, “equal” and “homogeneous” are equal states not only represent strictly equal states, but also have tolerances or differences with which the same function can be obtained. It also represents the existing state.
  • expressions representing shapes such as a square shape and a cylindrical shape not only indicate shapes such as a square shape and a cylindrical shape in a geometrically strict sense, but also within the range where the same effect can be obtained. Also, the shape including the uneven portion, the chamfered portion, and the like shall be indicated. Moreover, in the present specification, the expressions “comprising”, “including” or “having” one component are not exclusive expressions excluding the presence of other components.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aubre de turbine comprenant un corps d'aube et une pluralité de passages de refroidissement qui s'étendent dans le sens de la hauteur de l'aube dans ledit corps et communiquent entre eux, ce qui forme un passage d'écoulement en serpentin. Les passages de refroidissement sont pourvus d'un premier turbulateur disposé sur une surface de paroi interne d'un passage côté amont parmi la pluralité de passages de refroidissement, et un deuxième turbulateur disposé sur une surface de paroi interne d'un passage côté aval, parmi la pluralité de passages de refroidissement, disposé sur le côté aval du passage côté amont. L'aube de turbine selon l'invention se caractérise en ce qu'un deuxième angle formé par le deuxième turbulateur par rapport au sens d'écoulement d'un fluide de refroidissement dans le passage côté aval est inférieur à un premier angle formé par le premier turbulateur par rapport au sens d'écoulement du fluide de refroidissement dans le passage côté amont.
PCT/JP2018/038335 2017-11-09 2018-10-15 Aube de turbine et turbine à gaz WO2019093075A1 (fr)

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KR1020207007194A KR102350151B1 (ko) 2017-11-09 2018-10-15 터빈 블레이드 및 가스 터빈
DE112018004279.0T DE112018004279B4 (de) 2017-11-09 2018-10-15 Turbinenschaufel und gasturbine
US16/651,559 US11643935B2 (en) 2017-11-09 2018-10-15 Turbine blade and gas turbine
CN201880060063.2A CN111094701B (zh) 2017-11-09 2018-10-15 涡轮叶片及燃气轮机

Applications Claiming Priority (2)

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JP2017-216759 2017-11-09
JP2017216759A JP6996947B2 (ja) 2017-11-09 2017-11-09 タービン翼及びガスタービン

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JP (1) JP6996947B2 (fr)
KR (1) KR102350151B1 (fr)
CN (1) CN111094701B (fr)
DE (1) DE112018004279B4 (fr)
WO (1) WO2019093075A1 (fr)

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CN111094701B (zh) 2022-10-28
CN111094701A (zh) 2020-05-01
JP6996947B2 (ja) 2022-01-17
US11643935B2 (en) 2023-05-09
KR20200036023A (ko) 2020-04-06
DE112018004279B4 (de) 2024-10-17
JP2019085973A (ja) 2019-06-06
US20200263554A1 (en) 2020-08-20
DE112018004279T5 (de) 2020-05-14
KR102350151B1 (ko) 2022-01-11

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